TCDS A60EU

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 Rev. No. 40 37 37 23 25 31 38 39 32 37 39 37 32 39 39 39 39 39 40 39 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET NO. A60EU This data sheet which is part of Type Certificate No. A60EU prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder DAHER AIRCRAFT, SAS Immeuble BELAIA 7 Avenue de l’Union F-94310 ORLY Type Certificate Holder Record Name of the TC Holder is changed from DAHER AEROSPACE to DAHER AIRCRAFT, SAS on August 19, 2025 (see note 28) I. Model TBM 700, 6 PCLM (Normal Category) approved August 28, 1990. [See note 14, certification Basis section, and Equipment section for information on different versions and trade names of the TBM 700.] Engine Airplanes not equipped with modification No MOD. 70-0188-00 (see note 7): Pratt and Whitney of Canada, Ltd., PT6A-64 Turbo prop Airplanes equipped with modification No MOD. 70-0188-00 (see note 7): Pratt and Whitney of Canada, Ltd., PT6A-66D Turbo prop Airplanes equipped with modification No MOD. 70-0621-76: Pratt and Whitney of Canada, Ltd., PT6E-66XT Turbo prop Fuel Jet A, Jet A1, Jet B, JP4, JP5, JP8, anti-ice additive according to the specification MIL-I- 27686 E or specification MIL-I-85470 A in the following proportions: minimum content 0.06% by volume maximum content 0.15% by volume Engine Limits Airplanes not equipped with modification No MOD. 70-0188-00 (see note 7): Take-off and maximum continuous power 700 SHP Gas generator rotation speed 39 000 RPM (104.1 %) Propeller rotation speed 2 000 RPM Interturbine maximum temperature 800ºC Oil: minimum pressure 60 psi maximum pressure 135 psi maximum temperature 104ºC Airplanes equipped with modification No MOD. 70-0188-00 (see note 7) and not equipped with modification No MOD70-0357-7 (see note 23): Take-off power (flap extended) 700 SHP Maximum continuous power (flap up) 850 SHP Gas generator rotation speed 39 000 RPM (104.1 %) Propeller rotation speed 2 000 RPM Interturbine maximum temperature for take off 850ºC Interturbine maximum temperature for climb/cruise 840ºC Oil: minimum pressure 60 psi maximum pressure 135 psi maximum temperature 104ºC A60EU Revision 40 DAHER AIRCRAFT TBM 700 April 24, 2026 Page 2 of 20 Airplanes equipped with modification No MOD. 70-0188-00 (see note 7) and equipped with modification No MOD70-0357-71 (see note 23): Take-off power (flap extended) 850 SHP Maximum continuous power (flap up) 850 SHP Gas generator rotation speed 39 000 RPM (104.1 %) Propeller rotation speed 2 000 RPM Interturbine maximum temperature for take off 850ºC Interturbine maximum temperature for climb/cruise 840ºC Oil: minimum pressure 60 psi maximum pressure 135 psi maximum temperature 104ºC Airplanes equipped with modification No MOD. 70-0621-76 and modification No MOD70-0665-61: Take-off power (flap extended) 895 SHP Maximum continuous power (flap up) 895 SHP Gas generator rotation speed 39 000 RPM (104 %) Propeller rotation speed 1 925 RPM Interturbine maximum temperature for take off 850ºC Interturbine maximum temperature for climb/cruise 825ºC Oil: minimum pressure 60 psi maximum pressure 135 psi maximum temperature 104ºC Propeller and Propeller Limits Aircraft not equipped with optional SOCATA modification No MOD70-0345-61 HARTZELL Constant speed HC-E4N-3 / E9083 S (K) Diameter: not over 91 in., not under 90 in. Pitch setting at 30 in., sta.: Low 21º Feather 86º Reverse - 11º Aircraft equipped with optional SOCATA modification No MOD70-0345-61 HARTZELL Constant speed HC-E5N-3C / NC8834 K Diameter: not over 91 in., not under 90 in. Pitch setting at 30 in., sta.: Low 19.5º Feather 85º Reverse - 9º Aircraft equipped with optional SOCATA modification No MOD70-0665-61 HARTZELL Constant speed 5D31-NK366B1/86DB01B Diameter: not over 91 in., not under 90 in. Pitch setting at 30 in., sta.: Low 19.5º Feather 86.1º Reverse - 9.3º Airspeed Limits Aircraft not equipped with MOD70-0357-71 (see note 23): VMO (Maximum operating speed) 271 KCAS VA (Maneuvering speed) 160 KCAS VFE (Maximum flaps extended speed) Landing configuration 120 KCAS Takeoff configuration 180 KCAS VLO (Maximum landing gear operation speed) retraction 130 KCAS extension 180 KCAS VLE (Maximum landing gear extended speed) 180 KCAS Aircraft equipped with MOD70-0357-71(see note 23): VMO (Maximum operating speed) 270 KCAS VA (Maneuvering speed) 160 KCAS Page 3 of 20 VFE (Maximum flaps extended speed) Landing configuration 120 KCAS Takeoff configuration 180 KCAS VLO (Maximum landing gear operation speed) Retraction 151 KCAS extension 180 KCAS VLE (Maximum landing gear extended speed) 180 KCAS C.G. Range Airplanes not equipped with modification No. MOD 70-139-00 (see note 6): (+ 181.3) to (+ 194.9) at 4409 lbs. or less (+ 183.6) to (+ 194.9) at 6250 lbs. or less (+ 184.8) to (+ 194.3) at 6579 lbs. or less Straight line between points given. Airplanes equipped with modification No. MOD 70-139-00 (see note 6): (+ 181.3) to (+ 194.9) at 4409 lbs. or less (+ 183.6) to (+ 194.9) at 6250 lbs. (+ 185.3) to (+ 194.3) at 6579 lbs. (+ 187) forward limit at 7024 lbs. (+ 187) to (+ 193.65) at 7394 lbs. Straight line between points given. Airplanes equipped with modification No. MOD 70-680-10: (+ 181.3) to (+ 194.9) at 4409 lbs. or less (+ 183.6) to (+ 194.9) at 6250 lbs. (+ 185.3) to (+ 194.3) at 6579 lbs. (+194.0) aft limit at 6986 lbs. (+ 187) forward limit at 7024 lbs. (+ 187) to (+ 193.7) at 7394 lbs. (+ 193.4) to (+ 193.6) at 7615lbs. Straight line between points given. Empty Weight C.G. Range None Datum 118.11 in. ahead of firewall front face. Leveling Means Cabin floor mounting rail. Maximum Weight Airplanes not equipped with modification No. MOD 70-139-00 (see note 6): 6579 lbs.: takeoff 6250 lbs.: landing 6614 lbs.: ramp Airplanes equipped with modification No. MOD 70-139-00 (see note 6): 7394 lbs.: takeoff 7024 lbs.: landing 7430 lbs.: ramp Airplanes equipped with modification No. MOD 70-0680-10: 7615 lbs.: takeoff 7110 lbs.: landing 7650 lbs.: ramp Number of Seats & Maximum Baggage Airplanes not equipped with modification No. MOD70-0315-25 (see note 17) Standard version Seats limits 1 thru 6 seats Baggage Page 4 of 20 - In the front compartment: 110 lbs. at 128.0 See * 1 - Behind the cabin: 220 lbs. at 297.6 See * 2 - Behind the cabin: 220 lbs. at 303 100 lbs. at 303 See * 3 See * 4 - In the rear compartment: 77 lbs. at 340.9 See * 5 * 1: Valid S/N 1 to 243, except S/N 205 and 240 and from S/N 434. * 2: Valid S/N 1 to 23, 25, 28, 33 and 35, except airplanes equipped as a retrofit with modification No. MOD 70-019-25. * 3: Valid S/N 24, 26, 27, 29 to 32, 34, 36 to 9999, except airplanes equipped with modification No. MOD 70-139-00 (see note 6), plus airplanes equipped as a retrofit with modification No. MOD 70-019-25. * 4: Valid airplanes equipped with modification No. OPT 70-01-029 or modification No. MOD 70-139-00 (see note 6) * 5: Valid for airplanes equipped with modifications No. MOD 70-139-00 (see note 6) or MOD 70-140-00 Not valid for aiplanes equipped with modification No. MOD70-0207-00. 7- place accommodation A. Option No. OPT 70-25-002 A Seats limits 1 to 7 seats - L.H. and R.H. front seats at +180.5 - L.H. and R.H. intermediate seats at +216.8 - R.H. rear seat at +249.0 - two-place rear divan at +283.6 Baggage limits - In the front compartment: 110 lbs. at 128.0 - Behind the cabin: 77 lbs. at 309.0 B. Option No. OPT 70-25-002 B or Option No. OPT 70-25-002 C Seat Limits 1 to 7 seats - L.H. and R.H. front seats at +180.5 - L.H. intermediate seats at +223.1 - R.H. intermediate seats at +209.5 - R.H. rear seat at +239.5 - two place rear divan at +272.3 Baggage limits - In the front compartment: 110 lbs. at 128.0 - Behind the cabin: 77 lbs. at 303.0 Airplanes equipped with modification No. MOD70-0315-25 (see note 17) 6-seat accommodation Seats limits 1 thru 6 seats - 2 seats at +180.5 - 2 seats at +224.8 - 2 seats at +259.3 Baggage limits - In the front compartment: 110 lbs. at 128.0 - Behind the cabin: 220 lbs. at 297.6 4- seat accommodation Page 5 of 20 Seats limits 1 thru 4 seats - 2 seats at +180.5 - 2 seats at +224.8 Baggage limits - In the front compartment: 110 lbs. at 128.0 - Behind the cabin: 220 lbs. at 303.0 176 lbs. at 259.3 Fuel Capacity Airplanes not equipped with modification No. MOD 70-0211-57: 290.6 gal. (two 145.3 gal. at + 189.8 : 281.6 gal. usable) See Note 1 for weight and unusable fuel Airplanes equipped with modification No. MOD 70-0211-57: 301 gal. (two 150.5 gal. at + 189.8 : 292 gal. usable) See Note 1 for weight and unusable fuel Oil Capacity 12.7 qt (at + 82.3 - 6 qt unusable) See Note 1 for weight Maximum Operating Altitude Airplanes not equipped with modifications No. OPT 70-01-026 MOD 70-139-00 nor MOD 70-140-00: 30,000 ft. Airplanes equipped with modifications No. OPT 70-01-026 MOD 70-139-00 or MOD 70-140-00: 31,000 ft. Control Surface Movements Elevator (Angles references: stabilator chord) Nose-up attitude: 30º ± 1.5º Nose-down attitude: 10º ± 1º Stabilator tab (elevator at 0º) Nose-up attitude: 15º ± 1º Nose-down attitude: 20º ± 1º Roll - Ailerons (Reference: wing chord) up 15º ± 1º down 20º ± 1º - Spoiler (Reference: wing upper surface) up 58º +2°/-3° down 20.5º +1°/-5° - Tab up 14º ± 1º down 14º ± 1º Yaw control Rudder (Reference: fin chord) left turn 26º ± 1º right turn 35º ± 1.5º Rudder tab (Reference: rudder chord) left turn 13.5° ± 1° right turn 9.5° ± 1° Certification Basis Effective date of certification basis: January 15, 1987 Date of U.S. application: January 22, 1988 Type Certificate issued on August 28, 1990 Type Certification under 14 CFR Section 21.29 including the following requirements: Airplanes not equipped with modification No. MOD 70-139-00 (see note 6): - 14 CFR Part 23 effective February 1, 1965, including Amendments 23-1 through 23-34 and Sections 23.783, 23.811 and 23.807 of Amendments 36 Page 6 of 20 - 14 CFR Part 36 effective December 1, 1969, including Amendments 36-1 through Amendment 36-17. - Special Federal Aviation Regulation Number 27, effective February 1, 1974 including Amendments 27-1 through 27-6. Airplanes equipped with modification No. MOD 70-139-00 (see note 6): - 14 CFR Part 23 effective February 1, 1965, including Amendments 23-1 through 23-34, Sections 23.783, 23.811 and 23.807 of Amendments 36 and Sections 23.49, 23.561, 23.562 and 23.785 of Amendment 44. - 14 CFR Part 34 effective September 10,1990, including Amendments 34-1 through Amendment 34-3. - 14 CFR Part 36 effective December 1, 1969, including Amendments 36-1 through Amendment 36-22. Airplanes (s/n 434 -999, except 687) equipped with modification No. MOD 70 -0211-57 (“Fuel tanks extension”), modification No. MOD 70 -0176-00 (“Garmin G1000”), and optional modification No. MOD 70-0226-00 (“SVS” option to G1000) (see notes 8, 9, 10, 11, 12): - 14 CFR Part 23 effective February 1, 1965, including Amendments 23-1 through 23-34, Section 23.1301 of Amendment 23-20, Sections 23.783, 23.811 and 23.807 of Amendments 36, Sections 23.1322 and 23.1331 of Amendment 43, Sections 23.49, 23.561, 23.562 and 23.785 of Amendment 44, Sections 23.1309, 23.1311 23.1321, 23.1323, 23.1353, 23.1365 and 23.1431 of Amendment 49 and Section 23.1308 of Amendment 57. - 14 CFR Part 34 effective September 10, 1990, including Amendments 34-1 through Amendment 34-3. - 14 CFR Part 36 effective December 1, 1969, including Amendments 36-1 through Amendment 36-22. Airplanes (s/n 687, 1000 -1105) equipped with modification MOD 70 -0176-00 (“Garmin G1000”), modification No. MOD 70 -0234-24 (“New electrical generation and primary distribution”), MOD70-0322-00 (“Aerodynamic efficiency improvement”), MOD70- 0323-71 (“Propulsion efficiency improvement”), MOD70-0324-00 (“Human Machine Interface improvement”), MOD70-0357-71 (“Take-off and landing operations at 850SHP”), optional modification No MOD70-0345-61 (“New five-blade propeller”), optional modification No. MOD70-407-00 (“Aural alerts evolution and V15 Software for G1000 Integrated Flight Deck on TBM850/900“) and optional modification No. MOD70- 0407-00 Ed 2 Version C (“ESP and USP option to G1000”) (see notes 18, 19, 20, 21, 22 and 23): or Airplanes (s/n 1170-9999) equipped with modification MOD 70-0176-00 (“Garmin G1000”) and optional modification MOD70-0539-00 (“Garmin G1000 Nxi”), modification No. MOD 70-0234-24 (“New electrical generation and primary distribution”), MOD70-0322-00 (“Aerodynamic efficiency improvement”), MOD70- 0323-71 (“Propulsion efficiency improvement”), MOD70 -0324-00 (“Human Machine Interface improvement”), MOD70-0357-71 (“Take-off and landing operations at 850SHP”), optional modification No MOD70-0345-61 (“New five-blade propeller”), optional modification No. MOD70-407-00 (“Aural alerts evolution and V15 Software for G1000 Integrated Flight Deck on TBM850/900“) and optional modification No. MOD70- 0407-00 Ed 2 Version C (“ESP and USP option to G1000”) (see notes 18, 19, 20, 21, 22, 23, 24 and 25): - 14 CFR Part 23 effective February 1, 1965, including Amendments 23-1 through 23-34, Section 23.1301 of Amendment 23-20, Sections 23.783, 23.811 and 23.807 of Amendments 36, Sections 23.1322 and 23.1331 of Amendment 43, Sections 23.49, 23.561, 23.562 and 23.785 of Amendment 44, Sections 23.1309, 23.1311 23.1321, 23.1323, 23.1353, 23.1365 and 23.1431 of Amendment 49, Section 23.207 of Amendment 50, Section 23.1308 of Amendment 57 and Section 23.1306 of Amendment 61. (Note: Airplanes equipped with optional modification No. MOD70 - 0423-34 “Lift transducer and AOA” also include Section 23.207 of Amendment 50. Airplanes equipped with opti onal modification No. MOD70 -0388- 25 “AMSAFE Airbag Seatbelt on Pilot and Co-Pilot Seats” also include FAA Special Conditions No. 23-276-SC.) - 14 CFR Part 34 effective September 10,1990, including Amendments 34-1 through Amendment 34-3. - 14 CFR Part 36 effective December 1, 1969, including Amendments 36-1 Page 7 of 20 through Amendment 36-28. Airplanes (s/n 1111-1215) equipped with optional modification No. MOD70-0476-00 (“Garmin G3000” including ESP and USP option to G3000), modification No. MOD 70- 0234-24 (“New electrical generation and primary distribution”), MOD70-0322-00 (“Aerodynamic efficiency improvement”), MOD70-0323-71 (“Propulsion efficiency improvement”), MOD70-0324-00 (“Human Machine Interface improvement”), MOD70- 0357-71 (“Take-off and landing operations at 850SHP”) and optional modification No MOD70-0345-61 (“New five-blade propeller”) (see notes 18, 19, 20, 21, 22 and 23): or Airplanes (s/n 1216-9999) equipped with optional modification No. MOD70-0476-00 (“Garmin G3000” including ESP and USP option to G3000) and optional modification No. MOD70-0549-00 (“Garmin G3000 2018”), modification No. MOD 70-0234-24 (“New electrical generation and primary distribution”), MOD70-0322-00 (“Aerodynamic efficiency improvement”), MOD70-0323-71 (“Propulsion efficiency improvement”), MOD70-0324-00 (“Human Machine Interface improvement”), MOD70-0357-71 (“Take- off and landing operations at 850SHP”) and optional modification No MOD70-0345-61 (“New five-blade propeller”) (see notes 18, 19, 20, 21, 22, 23, 24 and 26): or Airplanes (s/n 1272, 1275-9999) equipped with optional modification No. MOD70 -0476- 00 (“Garmin G3000” including ESP and USP option to G3000), optional modification No. MOD70-0549-00 (“Garmin G3000 2018”) and optional modification No. MOD70 -0649- 00 (“G3000 system Software V21.25”), modification No. MOD 70-0234-24 (“New electrical generation and primary distribution”), MOD70-0322-00 (“Aerodynamic efficiency improvement”), MOD70-0323-71 (“Propulsion efficiency improvement”), MOD70-0324-00 (“Human Machine Interface improvement”), MOD70 -0357-71 (“Take- off and landing operations at 850SHP”), optional modification No MOD70-0345-61 (“New five-blade propeller”), modification No. MOD70-0550-00 (“Auto-throttle”), modification No. MOD70-0619-11 (“Modification of cabin interior markings”) and optional modification No. MOD70 -0632-34 (“Magnetometer MD032 integration”) (see notes 18, 19, 20, 21, 22, 23, 24, 31 and 32): or Airplanes (s/n 1333 -9999) equipped with optional modification No. MOD70 -0476-00 (“Garmin G3000” including ESP and USP option to G3000), optional modification No. MOD70-0549-00 (“Garmin G3000 2018”) and optional modification No. MOD70-0649- 00 Version E (G3000 system new Software SR 5.1.8) and optional modification No. MOD70-0650-34 (“Emergency Autoland/HomeSafe system”), modification No. MOD 70- 0234-24 (“New electrical generation and primary distribution”), MOD70-0322-00 (“Aerodynamic efficiency improvement”), MOD70-0323-71 (“Propulsion efficiency improvement”), MOD70-0324-00 (“Human Machine Interface improvement”), MOD70 - 0357-71 (“Take-off and landing operations at 850SHP”), optional modification No MOD70-0345-61 (“New five-blade propeller”), modification No. MOD70-0550-00 (“Auto-throttle”), modification No. MOD70 -0619-11 (“Modification of cabin interior markings”) and optional modification No. MOD70 -0632-34 (“Magnetometer MD032 integration”) (see notes 18, 19, 20, 21, 22, 23, 24, 31, 32 and 33): - 14 CFR Part 23 effective February 1, 1965, including Amendments 23-1 through 23-34, Section 23.1301 of Amendment 23-20, Sections 23.783, 23.811 and 23.807 of Amendments 36, Sections 23.1322 and 23.1331 of Amendment 43, Sections 23.49, 23.561, 23.562 and 23.785 of Amendment 44, Sections 23.1309, 23.1311 23.1321, 23.1323, 23.1353, 23.1365 and 23.1431 of Amendment 49, Section 23.207 of Amendment 50, Section 23.1308 of Amendment 57 and Section 23.1306 of Amendment 61. (Note: Airplanes equipped with optional modification No. MOD70 - 0423-34 “Lift transducer and AOA” also include Section 23.207 of Amendment 50. Section 1308 of Amendment57 and Section 23.1306 of Amendment 61. - 14 CFR Part 34 effective September 10,1990, including Amendments 34-1 through Amendment 34-3. - 14 CFR Part 36 effective December 1, 1969, including Amendments 36-1 through Amendment 36-28. Airplanes (s/n 1408-9999) equipped with modifications No. MOD70-0646-21 (“ENVIRO components based ECS”), modification No. MOD70 -0753-00 (“Software Upgrade”), modification No. MOD70-0680-10 (“Weight and balance modification”): - 14 CFR Part 23 effective February 1, 1965, including Amendments 23-1 through 23-34, Section 23.1301 of Amendment 23-20, Sections 23.783, 23.811 and 23.807 of Amendments 36, Sections 23.1322 and 23.1331 of Amendment 43, Sections Page 8 of 20 23.49, 23.561, 23.562 and 23.785 of Amendment 44, Sections 23.1309, 23.1311 23.1321, 23.1323, 23.1353, 23.1365 and 23.1431 of Amendment 49, Section 23.207 of Amendment 50, Section 23.1308 of Amendment 57 and Section 23.1306 of Amendment 61. (Note: Airplanes equipped with optional modification No. MOD70 - 0423-34 “Lift transducer and AOA” also include Section 23.207 of Amendment 50. Section 1308 of Amendment 57 and Section 23.1306 of Amendment 61. - 14 CFR Part 34 effective September 10,1990, including Amendments 34-1 through Amendment 34-3. - 14 CFR Part 36 effective December 1, 1969, including Amendments 36-1 through Amendment 36-28. Airplanes (s/n 140 8-9999) equipped with modifications No. MOD70-0621-76 (“Engine power increase, Engine control and e-Throttle”), modification No. MOD70-0665-61 (“Five blades Raptor Propeller”): - 14 CFR Part 23 at Amendment 23-64 sections 23.2005, 23.2010, 23.2105, 23.2115(a)(1)(2)(3)(b), 23.2120(a)(1)(2)(c), 23.2125, 23.2135, 23.2140, 23.2145, 23.2155, 23.2160, 23.2200, 23.2205, 23.2210, 23.2215, 23.2225, 23.2230, 23.2235, 23.2240(a)(b)(c)(1)(2), 23.2245, 23.2300, 23.2335, 23.2400(a)(b)(c)(1)(2)(3)(4)(e), 23.2405, 23.2410, 23.2415, 23.2420, 23.2425, 23.2500(a)(1)(2), 23.2505, 23.2510, 23.2515, 23.2520, 23.2525, 23.2600, 23.2605, 23.2610, 23.2615, 23.2620, Appendix A - 14 CFR Part 23, including Amendments 23-1 through Amendment 23-62. - -Sections 23.201, 23.203, 23.207, 23.221 - 14 CFR Part 34 effective September 10,1990, including Amendments 34-1 through Amendment 34-6. - 14 CFR Part 36 effective December 1, 1969, including Amendments 36-1 through Amendment 36-31, Appendix G. Equivalent Safety Items: Equivalent levels of safety finding made per the provisions of 14 CFR Part 21.21(b)(1) for: ELOS ACE-02-01: 14 CFR §23.807(a)(1), Emergency Exits; Refer to FAA letter dated October 7, 2001, applicable to cargo configured airplanes only (See Note 4.) ELOS ACE-14-01: 14 CFR §23.777(d) Cockpit Controls Location and 14 CFR §23.781(b), Shape – Single Power Lever for TBM 700 dated December 12, 2013, applicable to aircraft equipped with MOD70-0324-00 (see note 21) ELOS AT01004CE-A-P-2: 14 CFR §23.1305(e),(j, and (m), amendment 23-24, Part Time and Full Time Digital Only Powerplant Indications, applicable for aircraft equipped with MOD70-0550-00 (see note 31) ELOS AT01078CE-A-S-2: 14 CFR part 23 §23.671, 23.697, 23.729, 23.777, 23.779, 23.991, 23.1141, 23.1189, 23.1301, 23.1303, 23.1305, 23.1309, 23.1311, 23.1321, 23.1322, 23.1337, 23.1555, Airplanes equipped with DAHER modification No. MOD70-0650-34 (“Emergency Autoland/HomeSafe System”) s/n 1272, 1275-9999 ELOS AT11910IB-A-23.1303:14 CFR 21.21(b)(1), 23.1301, 23.1303, 23.1309, 23.1311, 23.1321, 23.1459 Indications removal from Primary Flight Displays during ground phase on Model Daher TBM700N airplane Airplanes equipped with DAHER modification No. MOD70-0876-00 Special Conditions: Special Condition per the provisions of 14 CFR Part 21.21(b)(1) for: Special Condition No. 23-276-SC Airbag seatbelt on Pilot and Co-Pilot Seats (See Note 24) Special Condition No. 23-296-SC Autothrust System effective August 30, 2019 (See Note 31) Approved for flight into known icing. Page 9 of 20 Direction Générale de l’Aviation Civile (DGAC) originally type certified this aircraft under its type certificate number TC 181, and EASA Type Certificate Number EASA.A.010. The FAA validated this product under U.S. Type Certificate Number A60EU. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of France. Serial Nos. Eligible Serial Numbers 0001-9999 Import Requirements A Certificate of Airworthiness for Export endorsed as noted in this section must be submitted for each individual aircraft for which application for U.S. certification is made. a) To be considered eligible for operation in the United States, each aircraft manufactured under this type certificate must be accompanied by a certificate of airworthiness for export or certifying statement endorsed by the exporting foreign civil airworthiness authority which states (in the English language): This aircraft conforms to its U.S. type design (type certificate number A60EU) and is in a condition for safe operation. b) The U.S. airworthiness certification basis for aircraft type certificated under FAR Section 21.29 and exported by the country of manufacture is FAR Sections 21.183 (c) or 21.185(c). c) The U.S. airworthiness certification basis for aircraft type certificated under FAR Section 21.29 exported from countries other than the country of manufacture (e.g., third party country) is FAR Section 21.183(d) or 21.183(b). The FAA can issue a U.S. airworthiness certificate based on an NAA Export Certificate of Airworthiness (Export C of A) signed by a representative of the Direction Générale de l’Aviation Civile (DGAC) on behalf of the European Community. The Export C of A should contain the following statement: ‘The aircraft covered by this certificate has been examined, tested, and found to comply with U.S. airworthiness regulations 14 CFR 23 approved under U.S. Type Certificate No. A60EU and to be in a condition for safe operation.’ Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used aircraft based on the scope of the agreement, to identify any required statements by the exporting authority on the export certificate of airworthiness (or equivalent document), and for procedures for coordinating exceptions to conformity